# FALCON 2000

No 337-R1
JANUARY 26, 2015 

# MANDATORY

ATA 33-11
LIGHTING

EXTERIOR LIGHTINGELECTRICAL BONDING OF WHELEN FIN TIP ANTICOLLISION LIGHT 

# FALCON SERVICE BULLETIN

Copyright © 2015 by Dassault Aviation All rights reserved. No part of this work may be reproduced or copied in any form or by any means without written permission

of Dassault Aviation.



### 554

### LIGHTING EXTERIOR LIGHTING ELECTRICAL BONDING OF WHELEN FIN TIP ANTI-COLLISION LIGHT

Initial issuance July 25, 2007 List of effective pages : 1 to 11

Erratum September 09, 2007 List of effective pages : 1 to 11 List of modified pages : 7

Revision 1 January 26, 2015 List of effective pages : 1 to 11 List of modified pages : 1 to 11 REASON: The Service Bulletin is now rendered mandatory.

This revision is not applicable to aircraft already modified per the initial issuance of this Service Bulletin. 

# FALCON 2000 F2000 -337

F2000 -33-11

### LIGHTING EXTERIOR LIGHTING ELECTRICAL BONDING OF WHELEN FIN TIP ANTI-COLLISION LIGHT

1. PLANNING INFORMATION
A. EFFECTIVITYThis Service Bulletin is applicable to FALCON 2000 aircraft equipped with a WHELEN fin tip anticollision light (without SATCOM fairing) per Service Bulletin F2000-44 (M331). B. REASON The investigation conducted on a Falcon 2000 aircraft that had been struck by lightning has shown that the electrical bonding of the fin tip anti-collision light may not be sufficient under certain circumstances, potentially resulting in damaging the aircraft wiring. The purpose of this Service Bulletin is to improve the electrical bonding of the WHELEN anti-collision light located on the fin tip. C. DESCRIPTION After removing the fin tip fairing, the operation consists of the following:

• to install an electrical bonding strip in two parts between the anti-collision light and a rib of the fin, • to modify the shield connection of the wiring. D. COMPLIANCE • This Service Bulletin is rendered mandatory by EASA Airworthiness Directive No. 2015-0006. • As prescribed by the Airworthiness Authorities of the country of registration of the aircraft. E. APPROVAL This Service Bulletin covers DASSAULT AVIATION modification F2000 M3036 that has been approved under the authority of DOA nr. EASA.21J.051. The technical content of this document is approved under the authority of DOA nr. EASA.21J.051. F. LABOR Estimated labor-hours: Refer to Service Bulletin Commercial Summary. NOTE: These labor-hours only concern the work described in this Service Bulletin and do not include other maintenance work that may be performed on this occasion.
G. MATERIAL - PRICE AND AVAILABILITY The modification kit may be obtained from either address listed below: Western hemisphere: DASSAULT FALCON JET CORP. SPARES DISTRIBUTION CENTER 200 RISER ROAD 

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Revision 1 Page 1 / 11DASSAULT AVIATION Proprietary DataLITTLE FERRY, NJ 07643 U.S.A. Telephone: • CANADA and U.S.A.: 1-800-800-4036 • MEXICO: 001-800-800-4036 • Other countries: 1-201-541-4809 Fax: • CANADA and U.S.A.: 1-800-800-4817 • MEXICO: 001-800-800-4817 • Other countries: 1-201-440-7021 Other continents: DASSAULT AVIATION Falcon Spares BOITE POSTALE N°101 AEROPORT DU BOURGET 93350 - LE BOURGET Cedex (FRANCE) Please contact your Dassault Aviation Account Representative Telephone: 33 (0)1.48.35.56.78 Fax: 33 (0)1.48.35.56.00 E/H dafsorder@dassault-aviation.com Price and availability on request. H. TOOLING - PRICE AND AVAILABILITY Normal maintenance tooling. I. WEIGHT AND BALANCE Change in weight: None. Change in balance with respect to 25% MAC: None. J. REFERENCES Aircraft Maintenance Manual: • GENERAL MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK 20-00-00-910-801 )

• PRINCIPLES AND CHECK OF THE ELECTRICAL BONDING ( Refer to TASK 20-20-00-910-801 ) • OPERATIONAL TEST OF THE EXTERIOR LIGHTING (Refer to TASK 33-40-00-710-801 ) Illustrated Parts Catalog: • ANTI-COLLISION LIGHTS (Refer to IPC fig. 33-40-10-50 ) • VERTICAL STABILIZER FIN TIP (Refer to IPC fig. 55-30-40-10 ) Service Bulletin F2000-44 "Lights - Navigation lights - Replacement of fin anti-collision light" K. OTHER PUBLICATIONS AFFECTED The following publications will be revised at a later date to account for the changes introduced by this Service Bulletin: 

# FALCON 2000 F2000 -337

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Revision 1 Page 2 / 11DASSAULT AVIATION Proprietary Data• Illustrated Parts Catalog. • Maintenance Manual. • Wiring Manual. 

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Revision 1 Page 3 / 11DASSAULT AVIATION Proprietary Data2. ACCOMPLISHMENT INSTRUCTIONS

A. PRELIMINARY STEPS (1) The aircraft must be in the maintenance configuration (Refer to TASK 20-00-00-910-801 ). (2) Remove the screws attaching upper fin tip fairing ( 322A ) (Refer to IPC fig. 55-30-40-10 , item 10). (3) Disengage upper fin tip fairing ( 322A ) , disconnect connector (322P) and remove upper fin tip fairing ( 322A ). (4) Removal of the light unit assembly (Refer to IPC fig. 33-40-10-50 ):

• Remove the PR bead coating the retainer (item 360) without removing the flexible gasket located underneath. • Remove the retainer, glass cover and seal (items 380, 390 and 400). • Remove the light unit assembly (screws item 130). NOTE: Remove and discard gasket (item 420) if installed. B. ANTI-COLLISION LIGHT ELECTRICAL BONDING In accordance with fig. 1 : (1) Cut out the run outs of the compound seal to obtain a plane mounting surface. (2) Set the mounting-base bonding strip (item 1), equipped with plate (item 8), into place on the fairing. Attach with two screws. (3) Fold the tab of the strip to a 90° angle with respect to the fairing’s rib. (4) Pin the strip assembly (items 2 and 3) to the fairing. (5) Position the strip assembly (items 2 and 3) in contact against the RH side panel of the fairing and on strip (item 1). If necessary, rework the shape of the strips to obtain proper contact. (6) Remove the strip assembly (items 2 and 3). (7) Install double-sided adhesive tape on the face coming in contact with bonding strip (item 1). (8) Re-install strip assembly (items 2 and 3). Pin to hold in contact against the fairing. (9) Install strip (item 1) over the strip assembly, pressing firmly at the contact area. (10) Remove the strip assembly (items 1, 2 and 3). (11) Counterdrill bonding strip (item 2) to a diameter of 0.1 in (2.5 mm). Disconnect the strips and discard the adhesive tape, remove all remaining adhesive. (12) Enlarge the holes drilled in the strips to a diameter of 0.126 in (3.2 mm). Assemble bonding strips (items 1 and 2) using rivets (item 4). Coat the faces of the strips with covering sealant making a bead at the contour edge with bead sealant

. (13) Clean the contact surfaces of the light unit assembly, of the strips, and of the fairing using MEK

. (14) Coat the strip assembly (items 2 and 3) with interlaying sealant

. (15) Connect and safety connector (4LX) to the light unit. (16) Set the strip assembly and the light unit assembly into place in the fairing and attach the light assembly to the fairing. Smooth out the PR in excess around the strips. 

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Revision 1 Page 4 / 11DASSAULT AVIATION Proprietary Data(17) Use a shim to wedge strip assembly (items 2 and 3) in contact against the fairing’s wall. Allow to cure. (18) Temporarily position the fairing at the fin tip and mark the location of strip (item 3). (19) Strip the paint off the fin tip rib at the location marked for strip (item 3). Protect the stripped area with alodine

. (20) Install the seal, glass cover, and the retainer ( Refer to IPC fig. 33-40-10-50 , items 400, 390 and 380). (21) Apply bead sealant around the retainer plate. C. MODIFYING THE WIRING Modify the shield connection in accordance with instructions depicted hereafter and using:

• fig. 2 on aircraft with serial numbers 1, 12, 16, 18, 22 and subsequent (modification F2000 M331 factory-applied),

• fig. 3 on aircraft with serial numbers 2 through 11, 13, 14, 15, 17 and 19 through 21 (with SB F2000-44, if applied),

Dimension A: • Connector with front extraction: 1.38 in (35 mm). • Connector with rear extraction: 1.97 in (50 mm). Self-soldering sleeves must be staggered at the extremity of the wiring assemblies so as to prevent a bulge on the bundle. INSTALLING SELF-SOLDERING SLEEVES

• After stripping the shielded cable and the ground lead wire, unwind the shielding braid of cable without overlapping the shielding strands

. • Position the self-soldering sleeve on the stripped part of the cable.

• Insert the stripped part of the ground lead wire on the inside of the solder preform. Make sure that the ground lead wire is installed against the guide provided for this purpose. 

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Revision 1 Page 5 / 11DASSAULT AVIATION Proprietary Data• With hot air or infrared generator equipped with an appropriate reflector, start heating the small diameter of the self-soldering sleeve, then move up to the solder preform until it melts and flows. Complete the operation on the large side of the self-soldering sleeve. It is recommended to position the solder preform at a 90° angle maximum in relation to the heat source. The solder must always be visible to the operator. • The insulating sheath of the shielded cable must not be blistered nor burnt. D. FINAL STEPS (1) Use a permanent ink pen to record the number of this Service Bulletin on "Service Bulletin Compliance" label (item 7). (2) Use interlaying sealant to bond the "Service Bulletin Compliance" label (item 7) to the inner skin of the fairing next to the P/N. (3) Connect connector (322P), place the fairing on the fin tip and attach the fairing. (4) Measure the electrical bonding across the anti–collision light retainer plate and the reference point located in the mechanic’s servicing compartment (Refer to TASK 20-20-00-910-801 ). The measured value must not exceed 2 mΩ (5) Perform the operational test of the upper anti-collision light (Refer to TASK 33-40-00-710-801 ). E. RECORDING Record compliance with this Service Bulletin in the appropriate aircraft documents. Fill out the card located at the end of the Service Bulletin and mail or fax it to Dassault Aviation or Dassault Falcon Jet, or fill out the electronic Service Bulletin reply form located in the ”Service Bulletin" page on the Falcon portal. 

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Revision 1 Page 6 / 11DASSAULT AVIATION Proprietary Data3. MATERIAL INFORMATION

A. MODIFICATION KIT KIT P/N SBF900EX0285A (1) Mechanical kit

KIT P/N SBF900EX0285A - Mechanical kit

NEW P/N Q

T Y KEY WORD INSTRUCTIONS DISPOSITION ITEM FIG

FGFB319100010 1 Mounting-base bonding strip Supply already assembled - (1-fig. 1) - FGFB319100038 1 Shim - (8-fig. 1) - FGFB319100036 1 Strip Supply already assembled - (2-fig. 1) - FGFB319100037A1 1 Strip - (3-fig. 1) - NAS1919M04S02WU 3 Rivet
See NOTE - (4-fig. 1) - 78753 1 Studded support - (5-fig. 1) - 78750-02 1 Clamp - (6-fig. 1) - 79160 1 "Service Bulletin Compliance" label - (7-fig. 1) -

NOTE: Not applicable to FALCON 2000. (2) Electrical kit

KIT P/N SBF900EX0285A - Electrical kit

NEW P/N Q

T Y KEY WORD INSTRUCTIONS DISPOSITION FIG

01EQTC0S20-05-119-18 1 Lug Ground 322J - fig. 2 - fig. 3 - 01C0K302-16S01 1 Contact Ground 322J - fig. 2 - fig. 3 - 01CAN210-1-20 1 #20 gauge wire L= 3.3 ft (1 m) Ground 322J - fig. 2 - fig. 3 - 01C0A54143FC16 4 Blanking pin 322J/P - fig. 2 - fig. 3 - 01EQTRB23-2R 1 Self-soldering sleeve 4LX - fig. 2 - fig. 3 - 01CAN210-1-22 1 #22 gauge CF wire L = 1 ft (0.3 m) - See NOTE 1 4LX - fig. 2 - fig. 3 -
01CAN203-1-22Y 1 #22 gauge KZ wire L = 1 ft (0.3 m) - See NOTE 2 01EQTC0S20A03-071-22 1 Lug 4LX - fig. 2 - fig. 3 - 01C0K345-16S01 2 Contact 4LX - fig. 2 - fig. 3 - 

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Revision 1 Page 7 / 11DASSAULT AVIATION Proprietary DataKIT P/N SBF900EX0285A - Electrical kit

NEW P/N Q

T Y KEY WORD INSTRUCTIONS DISPOSITION FIG

01EQTEC1-1 1 Insulating sleeve 322P - fig. 2 - fig. 3 - 01EQTEC1-1 4 Insulating sleeve - See NOTE 3 01EQTPRL08B01 1 Splice - See NOTE 3 GND322J-B 2 Black sleeve with white marking 01PR0TMS3-32BK 322J - fig. 2 - fig. 3 -
GND312J-B 2 Black sleeve with white marking 01PR0TMS3-32BK 312J - fig. 2 - fig. 3 -
A 1 Black sleeve with white marking 01PR0TMS3-32BK 4LX - fig. 2 - fig. 3 -
B 1 Black sleeve with white marking 01PR0TMS3-32BK 4LX - fig. 2 - fig. 3 -
78750-01 5 Clamp 4LX - fig. 2 - fig. 3 -

NOTE 1: Use on FALCON 2000. NOTE 2: Do not use on FALCON 2000. NOTE 3: Do not use on FALCON 2000 B. LOCAL PROCUREMENT As indicated in Consumable Products Manual (CPM):

• alodine

.
• interlaying sealant

.
• bead sealant

.
• covering sealant

.
• MEK or equivalent. • Green CELOMER varnish 6060B. • Locking wire. 

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Revision 1 Page 8 / 11DASSAULT AVIATION Proprietary DataFigure 1: ELECTRICAL BONDING STRIPS INSTALLATION 

# FALCON 2000 F2000 -337

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Revision 1 Page 9 / 11Figure 2: AIRCRAFT S/N 1, 12, 16, 18, 22 AND SUBSEQUENT (MODIFICATION F2000 M331 FACTORY APPLIED) 

# FALCON 2000 F2000 -337

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Revision 1 Page 10 / 11Figure 3: AIRCRAFT S/N 2 THROUGH 11, 13, 14, 15, 17 AND 19 THROUGH 21 WITH SB F2000-44 IF APPLIED



### END OF DOCUMENT 

# FALCON 2000 F2000 -337

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Revision 1 Page 11 / 11SERVICE BULLETINS COMPLIANCE FALCON 2000 A/C S/N

DASSAULT AVIATION Number ATA Number F2000 337 F2000 33 11 Coding: C complete compliance T partial compliance

Performed by: Remarks: Revision 1 Date: Signature:



### SERVICE BULLETINS COMPLIANCE
Would you be kind enough to inform us that this Service Bulletin is complied with: - For "Western Hemisphere", mail upper card (No postage necessary if mailed in the U.S.A.) or fax to Dassault Falcon Jet: 1-201-541-4700. - For "Other Continents", mail card herebelow or fax to Dassault Aviation: 33 (0)1.47.11.65.21. On the occasion, if other Service Bulletins have been simultaneously complied with could you complete the blank spaces provided for this purpose.



### APPLICATION DE BULLETINS DE SERVICE
Lorsque vous aurez applique ce Bulletin de Service sur votre avion, veuillez avoir l'amabilite de nous en informer: - Utiliser la carte reponse superieure pour continent americain (Dispensee de timbrage pour postage depuis les U.S.A.) ou le fax pour Dassault Falcon Jet : 1-201-541-4700. - Ou la carte reponse inferieure pour autres continents ou le fax pour Dassault Aviation : 33 (0)1.47.11.65.21. Eventuellement, si d'autres Bulletins de Service ont ete appliques simultanement, vous pouvez les mentionner dans les cases vierges prevues a cet effet.

APPLICATION DES BULLETINS DE SERVICE SERVICE BULLETINS COMPLIANCE FALCON 2000 A/C S/N

DASSAULT AVIATION Number Numero DASSAULT AVIATION ATA Number Numero ATA F2000 337 F2000 33 11 Coding: C complete compliance application totale T partial compliance application partielle

Performed by: Fait par: Remarks: Revision 1 Date: Signature: Remarques: Revision 1